Projectile



ecu 3, W. B. PROJECTILE Filed Feb. 22;. 1944 INVENTOR. Wznslow 19. P

flTTORNEY Patented Dec. 3, 1 946 PROJECTILE Winslow B. Pope, Detroit,Mich., assignor, by mesne assignments, to United States of America 2Claims. 1

This invention relates to projectiles and devices of the type adapted tobe projected through space by the reaction propulsion principle.

Various devices of the reaction propulsion or rocket type have beenheretofore proposed, among which there is one type which embodies atubular casing secured to the rearward end of the projectile proper forhousing the propelling charge and having its trailing end contoured toprovide an axially opening Venturi passage. In such a device, the gasesflowing through the Venturi passage, due to uneven burning of thecharge, or for other reasons, may flow slightly off center through theVenturi passage. Such ofi-center flow or shifting of the flow of gasesfrom truly axial flow during the flight of the projectile will cause theprojectile to deviate from a true predetermined course.

The object of the present invention is to provide a new and novelarrangement whereby to insure an even flow of gases from a rocket typeprojectile.

Another object is to provide a rocket type projectile with a rotary gasdischarging device adapted to provide for uniform axial flow of thepropelling gases.

A further object is to provide a novel arrangement for preventingpremature bursting of the casing which houses the propelling charge.

With the above and other objects in view, which will be apparent fromthe following descriptions to those skilled in the art to which theinvention appertains, the present invention consists of certain featuresof construction and combinations of parts to be hereinafter describedwith reference to the accompanying drawing, and then claimed.

In the drawing which illustrates a suitable embodiment of the presentinvention:

Figure 1 is a side elevation, partially in section, of the rocketprojectile,

Figure 2 is an enlarged rear end view of the projectile shown in Figure1, and

Figure 3 is a transverse section taken approximately on line 3--3 ofFigure 2.

Referring to the accompanying drawing, the rocket device selected forillustration includes a main projectile body 5 having a chamber 6 forthe reception of an explosive or other charge. A tubular casing l isthreadably or otherwise suitably secured to the rearward end of the body5, the casing having an internal shoulder B which supports a. plate-likemember 9. The platelike member 9 supports a cage, composed of the rodsIll and interconnecting end ring I I, which carries the propellingcharge, which as shown in the drawing may be in the form of sticks I 2of slow-burning powder or other suitable combustible material.

In accordance with the present invention, the conventional singleaxially opening Venturi passage, such as shown in the copendingapplication, Serial No. 487,689, filed by Warren H. Farr on May 20,1943, has been replaced by a multi-jet rotary device l3.

To this end, the rearward end of the casing 5 is slightly reduced indiameter and provided with an internal shoulder l4. Inserted from therearward end of the casing and seated against the shoulder M is anannular ball thrust bearing 15. The cylindrical rotary dc /ice l3 seatsagainst the outer race of the bearing I5 and is mounted within therearward end of the casing for free rotation by means ofcircumferentially surrounding rollers l6, commonly known as needlebearings, the bearings I6 engaging with the inner wall of the rear endof the casing 5 and being seated in a circumferential recess l1 formedin the peripheral wall of the rotary device IS.

The device I3 is retained within the casing by means of a radiallyinwardly flanged ring 22 externally threaded to the end of the casing asshown in the drawing.

The rotary device I3 is provided with a plurality of uniformlycircumferentially spaced Venturi passages I8 arranged therein at anangle to the axis of the device I3. The passages It may be formed bydrilling and then taper reaming the drilled openings from the oppositesides of the rotary device to provide the restriction ill in thepassages l8.

It will be obvious that the flow through the passages l8 of the productsof combustion of the combustible propelling charge will, by reason ofthe angularly arranged passages I8, cause the device l3 to rotate. Sincethe device I3 is coaxial with the casing 5 and the gases dischargethrough the equally spaced jets, each the same distance from the axis ofrotation, the gases will leave the device in an annular rotating streamtruly coaxial with the casing thus insuring a uniform annular propellingpressure at all times.

In order to prevent the building up of a pressure within the casingprematurely which might tend to rupture the casing before the'device hasleft the projector and thereby cause serious damage, the rotary deviceI3 is provided with a central passage 20 which is counterbored at itsinner end to receive a plate 2| having a press fit therewith. The plate2| is of less yield strength than the casing wall and is oi suchpredetermined strength that in the event of the building up of abnormalor excessive pressures within the casing, it will rupture or blow out torelieve the pressure within the casing before it can reach a value whichwill rupture the casing.

The present invention is applicable to any re action propulsion devicewhether it be for an explosive projectile, a chemical device or anyother arrangement adapted to be projected through space.

Various changes may be made in the detailed an annular end thrustbearing within said end in advance oi. said member and engagedtherewith, and means secured to said end for retaining said member insaid end, said member having a plurality of discharge passages extending1ongitudinaliy therethrough, said passages being inclined relative tothe axis of rotation of said member and said axis oi rotation beingcoincident with the axis of said casing.

2. In a reaction propulsion device, a casing for housing a combustiblepropelling charge, a cylindrical member within one end of said casingand having a plurality of circumferentiaily spaced Jet passagesextending therethrough into communication with the interior of saidcasing, said memher having an axial opening therein, and a plate closingsaid opening at the end adjacent the interior of said casing, said platebeing or a material having a yield strength less than the yield strengthof said casing whereby incident to excessive pressures within saidcasing said plate will rupture prior to said casing.

WINSLOW B. POPE.

